Rotor blade sailing, which is characterized by excessive deflection of rotor blades, can be experienced by shipboard helicopters during rotor start-up and shut-down. In an attempt to model the complete ship-helicopter-rotor system in a way that is geometrically representative and computationally efficient, the system was represented as a discrete-property rigid-body and flexible-element system capable of simulating many important dynamic effects that contribute to the motion of rotor blades. This paper describes the model in detail and discusses validation cases. While both dynamic effects and aerodynamic effects are believed to be important components of blade sailing, this paper focuses exclusively on the dynamics. The validation cases discussed herein suggest that the modeling approach presented offers excellent potential for efficiently modeling blade sailing and other blade motion phenomena.
Skip Nav Destination
Article navigation
November 2008
Research Papers
Modeling Helicopter Blade Sailing: Dynamic Formulation and Validation
A. S. Wall,
A. S. Wall
Department of Mechanical and Aerospace Engineering,
Carleton University
, 1125 Colonel By Drive, Ottawa, ON, K1S 5B6, Canada
Search for other works by this author on:
F. F. Afagh,
F. F. Afagh
Department of Mechanical and Aerospace Engineering,
Carleton University
, 1125 Colonel By Drive, Ottawa, ON, K1S 5B6, Canada
Search for other works by this author on:
R. G. Langlois,
R. G. Langlois
Department of Mechanical and Aerospace Engineering,
Carleton University
, 1125 Colonel By Drive, Ottawa, ON, K1S 5B6, Canada
Search for other works by this author on:
S. J. Zan
S. J. Zan
Aerodynamics Laboratory,
Institute for Aerospace Research
, National Research Council of Canada, 1200 Montreal Road, Ottawa, ON, K1A 0R6, Canada
Search for other works by this author on:
A. S. Wall
Department of Mechanical and Aerospace Engineering,
Carleton University
, 1125 Colonel By Drive, Ottawa, ON, K1S 5B6, Canada
F. F. Afagh
Department of Mechanical and Aerospace Engineering,
Carleton University
, 1125 Colonel By Drive, Ottawa, ON, K1S 5B6, Canada
R. G. Langlois
Department of Mechanical and Aerospace Engineering,
Carleton University
, 1125 Colonel By Drive, Ottawa, ON, K1S 5B6, Canada
S. J. Zan
Aerodynamics Laboratory,
Institute for Aerospace Research
, National Research Council of Canada, 1200 Montreal Road, Ottawa, ON, K1A 0R6, CanadaJ. Appl. Mech. Nov 2008, 75(6): 061004 (10 pages)
Published Online: August 15, 2008
Article history
Received:
September 21, 2006
Revised:
May 2, 2008
Published:
August 15, 2008
Citation
Wall, A. S., Afagh, F. F., Langlois, R. G., and Zan, S. J. (August 15, 2008). "Modeling Helicopter Blade Sailing: Dynamic Formulation and Validation." ASME. J. Appl. Mech. November 2008; 75(6): 061004. https://doi.org/10.1115/1.2957599
Download citation file:
Get Email Alerts
Cited By
Hamiltonian System-Based Symplectic Framework for Analytical Vibration Analysis of Microplates
J. Appl. Mech (December 2024)
Related Articles
Modeling of Cross-Coupling Responses on Hingeless Helicopters via Gyroscopic Effect
J. Comput. Nonlinear Dynam (April,2012)
Adjoint Harmonic Sensitivities for Forced Response Minimization
J. Eng. Gas Turbines Power (January,2006)
A Time-Domain Harmonic Balance Method for Rotor/Stator Interactions
J. Turbomach (January,2012)
Movement of Deposited Water on Turbomachinery Rotor Blade Surfaces
J. Turbomach (April,2007)
Related Proceedings Papers
Related Chapters
Introduction
Turbine Aerodynamics: Axial-Flow and Radial-Flow Turbine Design and Analysis
Regression Based Neural Network for Studying the Vibration Control of the Rotor Blade for Micro-Unmanned Helicopter
International Conference on Mechanical and Electrical Technology, 3rd, (ICMET-China 2011), Volumes 1–3
Helicopter Rotor Blades
Applications of Composite Materials